In one implementation, a method for a solar cell array is provided, the method includes emitting a communication message from the solar cell array by reverse biasing the solar cell array so as to cause at least a portion of the solar array to emit a detectable amount of radiation corresponding to the communication message.
A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p.ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64D 31/00 - Commande des groupes moteurs; Leur disposition
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
4.
Methods and Systems for Determining Flight Plans for Vertical Take-Off and Landing (VTOL) Aerial Vehicles
Systems, devices, and methods for receiving, by a processor having addressable memory, data representing a geographical area for imaging by one or more sensors of an aerial vehicle; determining one or more straight-line segments covering the geographical area; determining one or more waypoints located at an end of each determined straight-line segment, where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds connecting each of the straight-line segments, where each turnaround comprises one or more connecting segments; and generating, by the processor, a flight plan for the aerial vehicle comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
In one possible embodiment, a wireless network with dynamic transmission control is provided that includes a multiple of nodes. The nodes include an arbiter and multiple client nodes. The arbiter is configured to control an operation of the client nodes by defining communications operation cycles and allocating a bandwidth to each of the client nodes on a cycle by cycle basis in response to requests for bandwidth from the client nodes.
H04W 72/543 - Critères d’affectation ou de planification des ressources sans fil sur la base de critères de qualité sur la base de la qualité demandée, p.ex. QdS [QoS]
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
B64C 27/26 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64D 27/06 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à pistons à l'intérieur de la voilure ou fixés à celle-ci
A system having a damper with six or more indentations on alternating sides of the damper, where each indentation is open to an outer circumferential surface of the damper and extends over halfway through a width of the damper, and six or more slots, each slot open to an undulating inner circumferential surface of the damper and extending through the width of the damper.
H02K 5/24 - Enveloppes; Enceintes; Supports spécialement adaptés pour la réduction ou à la suppression des bruits ou vibrations
F16F 1/376 - Ressorts faits d'un matériau à friction intérieure élevée caractérisés par une forme particulière présentant des saillies, des bossages, des dentelures ou similaires sur au moins une surface
F16F 1/38 - Ressorts faits d'un matériau à friction intérieure élevée avec manchon de matériau élastique entre un manchon extérieur rigide et un étui intérieur rigide ou une broche
F16F 15/08 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques avec ressorts en caoutchouc
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objets; Moyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p.ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
10.
SURVEY MIGRATION SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)
A method of migrating unmanned aerial vehicle (UAV) operations between geographic survey areas, including: uploading a first plurality of flight missions into a first UAV pod; deploying the UAV pod; autonomously launching the UAV from the UAV pod a plurality of times to perform the first plurality of flight missions; providing first survey data from the UAV to the UAV pod; autonomously migrating the UAV from the first UAV pod to a second UAV pod; receiving a second plurality of flight missions in a second UAV pod; providing the UAV with one of the second plurality of flight missions from the second UAV pod; autonomously launching the UAV from the second UAV pod a plurality of times to perform the second plurality of flight missions; and providing a second survey data from the UAV to the second UAV pod; where the autonomous migrating of the UAV to accomplish the first and second survey data happens autonomously and without active human intervention.
B60L 53/30 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange d'éléments d’emmagasinage d'énergie dans les véhicules électriques - Détails de construction des stations de charge
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64F 1/22 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manœuvre des aéronefs
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
Systems, devices, and methods for determining, by a processor, an unmanned aerial system (UAS) position relative to at least one flight boundary; and effecting, by the processor, at least one flight limitation of a UAS if the determined UAS position crosses the at least one flight boundary.
Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.
Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.
A system and method for transmitting still images and a video feed from an unmanned aerial vehicle to a ground station is disclosed. The system includes an aircraft including a digital video camera to capture still images and video frames of an object. A video encoder is coupled to the camera to provide a video output including video packets. A file server is coupled to the camera to provide a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the image data packets. A transmitter sends the data transmission to the ground station. The ground station receives the data transmission and demultiplexes the packets into separate video and image data packets. The ground control station may select the ratio the video stream images in relation to the still image to be transmitted from the aircraft.
H04N 23/60 - Commande des caméras ou des modules de caméras
H04N 23/661 - Transmission des signaux de commande de la caméra par le biais de réseaux, p. ex. la commande via Internet
H04N 21/236 - Assemblage d'un flux multiplexé, p.ex. flux de transport, en combinant un flux vidéo avec d'autres contenus ou données additionnelles, p.ex. insertion d'une adresse universelle [URL] dans un flux vidéo, multiplexage de données de logiciel dans un flu; Remultiplexage de flux multiplexés; Insertion de bits de remplissage dans le flux multiplexé, p.ex. pour obtenir un débit constant; Assemblage d'un flux élémentaire mis en paquets
H04N 21/434 - Désassemblage d'un flux multiplexé, p.ex. démultiplexage de flux audio et vidéo, extraction de données additionnelles d'un flux vidéo; Remultiplexage de flux multiplexés; Extraction ou traitement de SI; Désassemblage d'un flux élémentaire mis en paquets
15.
POD LAUNCH AND LANDING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS)
An unmanned aerial vehicle (UAV) storage and launch system, including: a UAV pod having an interior; and a telescoping UAV landing surface disposed in the interior of the UAV pod; where the telescoping UAV landing surface may translate up toward a top opening of the UAV pod, translate down into an interior of the UAV pod, or rotate relative to the UAV pod.
B64F 1/22 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manœuvre des aéronefs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
B64F 1/02 - Dispositifs d'arrêt; Barrières à freinage hydraulique
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
A lidar system, including a base, a sensor body, and a motor having a shaft. The motor is affixed to the base, and can drive the sensor body in rotation with respect to the base. An LED device and a light sensor are each mounted upon the sensor body. A data processing device is also mounted upon the sensor body, and is programmed to produce range information based upon the sensor data. The shaft carries two slip rings. The LED, the sensor and the data processing device all receive electrical power via the two slip rings. The data processing device is configured to transmit the range information via the two slip rings using pulse width modulation.
A method and system including: defining a geographic area; receiving a plurality of images; determining a plurality of image points; partitioning the geographic area into a plurality of image regions based on the plurality of image points; and stitching the plurality of images into a combined image based on the plurality of image regions.
A method and system including: an aerial vehicle including: a first camera comprising a first sensor having at least red, green, and blue color channels, where the blue color channel is sensitive to near-infrared (NIR) wavelengths; a first optical filter disposed in front of the first sensor, wherein the first optical filter is configured to block wavelengths below green, between red and NIR, and longer wavelength NIR; a processor having addressable memory in communication with the first camera, where the processor is configured to: capture at least one image of vegetation from the first camera; provide red, green, and NIR color channels from the captured image from the first camera; and determine at least one vegetative index based on the provided red, green, and NIR color channels.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
F01N 3/20 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour rendre les gaz d'échappement inoffensifs par conversion thermique ou catalytique des composants nocifs des gaz d'échappement caractérisés par les méthodes d'opération; Commande spécialement adaptés à la conversion catalytique
F01N 9/00 - Commande électrique des appareils de traitement des gaz d'échappement
F02B 33/40 - Moteurs avec pompes autres que celles du type à piston alternatif avec pompes rotatives du type à déplacement non positif
F02B 37/013 - Moteurs caractérisés par l'utilisation de pompes entraînées au moins temporairement par les gaz d'échappement les pompes entraînées par les gaz d'échappement étant disposées en série
F02B 37/18 - Commande des pompes par dérivation des gaz d'échappement
F02B 37/20 - Commande des pompes en augmentant l'énergie d'échappement, p.ex. en utilisant des chambres de combustion
F02B 43/10 - Moteurs ou ensembles fonctionnels caractérisés par l'utilisation d'autres gaz spécifiques, p.ex. l'acétylène, le gaz oxhydrique
F02B 73/00 - Combinaisons de plusieurs moteurs non prévues ailleurs
F02D 19/02 - Commande des moteurs caractérisés par l'emploi de combustible non liquide, de combustibles multiples ou de substances non combustibles ajoutées au mélange carburant particulière aux moteurs fonctionnant avec des combustibles gazeux
F02D 29/06 - Commande de moteurs, cette commande étant particulière aux dispositifs entraînés, ces dispositifs étant autres que des organes ou accessoires essentiels à la marche du moteur, p.ex. commande de moteur par des signaux extérieurs particulière aux moteurs entraînant des groupes électrogènes
F02D 41/00 - Commande électrique de l'alimentation en mélange combustible ou en ses constituants
F02M 21/02 - Appareils pour alimenter les moteurs en combustibles non liquides, p.ex. en combustibles gazeux stockés sous forme liquide en combustibles gazeux
F02D 41/06 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections pour des conditions particulières de fonctionnement pour le démarrage ou le réchauffage du moteur
F02D 41/08 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections pour des conditions particulières de fonctionnement pour le ralenti
F02D 41/14 - Dispositions de circuits pour produire des signaux de commande introduisant des corrections à boucle fermée
An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.
Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.
Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.
B64C 9/16 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction formant des fentes à l'arrière de l'aile
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 13/38 - Dispositifs de transmission avec amplification de puissance
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 3/24 - Structures moulées ou venues de fonderie
B64C 3/36 - Structures adaptées pour réduire les effets de l'échauffement aérodynamique ou les effets d'un échauffement externe d'une autre origine
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
25.
SYSTEM FOR DETACHABLY COUPLING AN UNMANNED AERIAL VEHICLE WITHIN A LAUNCH TUBE
An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 5/12 - Surfaces stabilisatrices réglables pour escamotage contre ou à l'intérieur du fuselage ou du fuseau-moteur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 9/36 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
28.
System for protecting a rotatable shaft of a motor from excessive bending moments
A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p.ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
In one implementation, a method for a solar cell array is provided, the method includes emitting a communication message from the solar cell array by reverse biasing the solar cell array so as to cause at least a portion of the solar array to emit a detectable amount of radiation corresponding to the communication message. In one embodiment a solar cell array circuit is provided including a solar string comprising a plurality of solar cells coupled together, a charge storage device coupled to a power bus, and a bidirectional boost-buck converter having a first and second pair of MOSFETs connected in series between positive and negative rails of the power bus with an inductor coupled from between the first and second paired MOSFETs to a charging output of the solar string.
Described is a method of delivery for cargo or goods from an aerial vehicle (mothership) to a designated ground delivery location via the use of a direct air shipping package. For example, an aerial vehicle may be an airplane or helicopter that remains at altitude with a package stowed for deployment. As the mothership travels in the vicinity of the designated location the package flight control computer (flight controller) calculates a preferred travel trajectory based upon the aerodynamic properties of the package and location relative to the designated delivery location such as a small delivery pad located on a patio of a home. When the mothership transits through a calculated release point the package disengages the mothership. As the package descends it may increase accuracy relative to the designated delivery location by altering aerodynamic properties to maintain the preferred travel trajectory and decreasing landing zone size requirements and increasing precision of delivery. To reduce the impact force at landing the designated delivery location and/or the package may contain a net, airbag, parachute or similar device to provide a suitably soft landing suitable for commercial home delivery.
In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.
Systems, devices, and methods that may include: determining one or more take-off variables for a vertical take-off and landing (VTOL) aerial vehicle; increasing an altitude of the VTOL aerial vehicle to a first altitude, where increasing the altitude comprises substantially vertical flight of the VTOL aerial vehicle; performing a first pre-rotation check of the VTOL aerial vehicle; adjusting a pitch of the VTOL aerial vehicle to a first pitch angle via motor control; adjusting the pitch of the VTOL aerial vehicle to a second pitch angle via at least one of: motor control and one or more effectors; and adjusting the pitch of the VTOL aerial vehicle to a third pitch angle via the one or more effectors, where the third pitch angle is substantially perpendicular to a vertical plane.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
33.
SYSTEM AND METHOD FOR INTERCEPTION AND COUNTERING UNMANNED AERIAL VEHICLES (UAVS)
Systems, devices, and methods for identifying a target aerial vehicle, deploying an interceptor aerial vehicle comprising at least one effector, maneuvering the interceptor aerial vehicle to a position to engage a target aerial vehicle, deploying the at least one effector to intercept the target aerial vehicle, and confirming that the target aerial vehicle has been intercepted.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
F41H 11/02 - Installations ou systèmes de défense anti-aérienne ou antimissiles
F41G 9/00 - Systèmes de commande des missiles ou projectiles, non prévus ailleurs
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
F41H 13/00 - Moyens d'attaque ou de défense non prévus ailleurs
In one possible implementation, a motor is provided including a rotor and a stator. Front cooling fins are thermally coupled to a front of the stator, and rear cooling fins are thermally coupled to a rear portion of the stator. The winding is between the front and rear cooling fins.
H02K 3/14 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre disposés dans des encoches avec des conducteurs transposés, p.ex. des conducteurs torsadés
H02K 3/47 - Enroulements à espace d'air, c. à d. enroulements ne comportant pas de noyau de fer
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
H02K 16/02 - Machines avec un stator et deux rotors
H02K 9/14 - Dispositions de refroidissement ou de ventilation dans lesquels l'agent de refroidissement gazeux circule entre l'enveloppe de la machine et une chemise extérieure
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/02 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine
H02K 3/30 - Enroulements caractérisés par leur matériau d'isolement
H02K 3/32 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement
35.
Interactive weapon targeting system displaying remote sensed image of target area
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 5/12 - Surfaces stabilisatrices réglables pour escamotage contre ou à l'intérieur du fuselage ou du fuseau-moteur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 9/36 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.
G05D 1/12 - Commande pour la recherche d'un objectif
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
F41G 9/00 - Systèmes de commande des missiles ou projectiles, non prévus ailleurs
An unmanned aerial vehicle (UAV) includes a fuselage, a gimbal-mounted turret having one or more degrees of freedom relative to the fuselage, a camera disposed in the gimbal-mounted turret for motion therewith in the one or more degrees of freedom, and a central video image processor disposed exteriorly of the gimbal-mounted turret, the central video image processor configured to receive and process image data from the camera.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
Systems, devices, and methods including one or more rib mounting flanges, where each rib mounting flange comprises: a spar opening configured to receive a main spar of a wing panel; one or more holes for receiving cross-bracing cables; and one or more holes for receiving cross-bracing cables; and one or more holes for connecting the rib mounting flange to an adjacent rib mounting flange.
Systems, devices, and methods including a leading edge tubular member; an upper tubular member; a lower tubular member; one or more upper rib members connected between the leading edge tubular member and the upper tubular member; one or more lower rib members connected between the leading edge tubular member and the lower tubular member; a rigid sandwich shell disposed between the upper tubular member and the leading edge tubular member; and a sandwich shear web disposed between the upper tubular member and the lower tubular member; where the rigid sandwich shell and the sandwich shear web form a D-shape.
Systems, devices, and methods for determining, by a processor, an unmanned aerial system (UAS) position relative to at least one flight boundary; and effecting, by the processor, at least one flight limitation of a UAS if the determined UAS position crosses the at least one flight boundary.
A system and method for transmitting still images and a video feed from an unmanned aerial vehicle to a ground station is disclosed. The system includes an aircraft including a digital video camera to capture still images and video frames of an object. A video encoder is coupled to the camera to provide a video output including video packets. A file server is coupled to the camera to provide a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the image data packets. A transmitter sends the data transmission to the ground station. The ground station receives the data transmission and demultiplexes the packets into separate video and image data packets. The ground control station may select the ratio the video stream images in relation to the still image to be transmitted from the aircraft.
H04N 23/60 - Commande des caméras ou des modules de caméras
H04N 23/661 - Transmission des signaux de commande de la caméra par le biais de réseaux, p. ex. la commande via Internet
H04N 21/236 - Assemblage d'un flux multiplexé, p.ex. flux de transport, en combinant un flux vidéo avec d'autres contenus ou données additionnelles, p.ex. insertion d'une adresse universelle [URL] dans un flux vidéo, multiplexage de données de logiciel dans un flu; Remultiplexage de flux multiplexés; Insertion de bits de remplissage dans le flux multiplexé, p.ex. pour obtenir un débit constant; Assemblage d'un flux élémentaire mis en paquets
H04N 21/434 - Désassemblage d'un flux multiplexé, p.ex. démultiplexage de flux audio et vidéo, extraction de données additionnelles d'un flux vidéo; Remultiplexage de flux multiplexés; Extraction ou traitement de SI; Désassemblage d'un flux élémentaire mis en paquets
44.
SYSTEMS AND METHODS FOR STARTING A SENSORLESS MOTOR
Systems, devices, and methods for: an unmanned aerial vehicle (UAV); at least one sensorless motor of the UAV, the at least one sensorless motor comprising a set of windings and a rotor; at least one propeller connected to the at least one sensorless motor; a microcontroller in communication with the at least one sensorless motor, wherein the microcontroller is configured to: determine a rotation rate of the at least one propeller; determine a rotation direction of the at least one propeller; provide an output to stop the at least one propeller if at least one of: the determined rotation rate is not a desired rotation rate and the determined rotation direction is not a desired rotation direction; and provide an output to start the at least one propeller if the at least one propeller is stopped at the desired rotation rate and the desired rotation direction.
G01P 3/48 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés
G01P 13/04 - Indication du sens positif ou négatif d'un mouvement linéaire ou du sens horaire ou anti-horaire d'un mouvement de rotation
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
H02P 6/182 - Dispositions de circuits pour détecter la position sans éléments séparés pour détecter la position utilisant la force contre-électromotrice dans les enroulements
45.
Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.
Systems, devices, and methods including at least one flight control computer (FCC) associated with at least one UAV, where the at least one FCC is configured to: determine a direction of travel of the at least one UAV relative to the Sun; adjust a UAV airspeed to a first airspeed if the determined direction of travel is towards the Sun; and adjust the UAV airspeed to a second airspeed if the determined direction of travel is away the Sun; where the first airspeed is greater than the second airspeed to maximize solar capture of a solar array covering at least a portion of the UAV.
H02S 20/32 - Structures de support mobiles ou réglables, p.ex. pour réglage de l’angle spécialement adaptées pour le suivi du soleil
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
48.
Vertical take-off and landing (VTOL) winged air vehicle with complementary angled rotors
Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
B64C 27/26 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64D 27/06 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à pistons à l'intérieur de la voilure ou fixés à celle-ci
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV using at least one electric motor, providing primary vertical lift for the UAV during the forward flight using a fixed and non-rotating wing, repositioning the at least one electric motor to provide vertical thrust during transition of the UAV to vertical flight for descent, landing the UAV on a surface using a vertical approach after the motor repositioning, and deploying an anchor to secure the UAV to a surface.
B64U 50/13 - Propulsion utilisant des soufflantes ou des hélices externes
B64U 50/19 - Propulsion utilisant des moteurs électriques
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
A system having a damper with six or more indentations on alternating sides of the damper, where each indentation is open to an outer circumferential surface of the damper and extends over halfway through a width of the damper, and six or more slots, each slot open to an undulating inner circumferential surface of the damper and extending through the width of the damper.
H02K 5/24 - Enveloppes; Enceintes; Supports spécialement adaptés pour la réduction ou à la suppression des bruits ou vibrations
F16F 1/376 - Ressorts faits d'un matériau à friction intérieure élevée caractérisés par une forme particulière présentant des saillies, des bossages, des dentelures ou similaires sur au moins une surface
F16F 1/38 - Ressorts faits d'un matériau à friction intérieure élevée avec manchon de matériau élastique entre un manchon extérieur rigide et un étui intérieur rigide ou une broche
F16F 15/08 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens élastiques avec ressorts en caoutchouc
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objets; Moyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p.ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
51.
Method Of Flight Plan Optimization Of A High Altitude Long Endurance Aircraft
Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV); at least one flight control computer (FCC) associated with each UAV, where the FCC controls movement of each UAV; at least one computing device associated with a ground control station; where the at least one FCC maintains a first flight pattern of a respective UAV of the at least one UAV above the ground control station; where the at least one computing device is configured to transmit a transition signal to the at least one FCC to transition the respective UAV of the at least one UAV from the first flight pattern to a second flight pattern in response to a wind speed exceeding a set threshold relative to a flight speed of the respective UAV of the at least one UAV.
Systems, devices, and methods including at least one computing device associated with a ground control station, the at least one computing device configured to: determine a starting position for an unmanned aerial vehicle (UAV) descent based on one or more local weather conditions; determine a flight pattern for landing the UAV based on the determined starting position for the UAV; and modify the determined flight pattern based on a change in the one or more local weather conditions and a current position of the UAV.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
53.
Method Of Managing A Fleet Of High Altitude Long Endurance Aircraft
Systems, devices, and methods for a fleet of three or more unmanned aerial vehicles (UAVs), where each UAV of the fleet of UAVs comprise a respective flight control computer (FCC); at least one computing device at a ground control station, where each computing device is in communication with each FCC, and where each computing device is associated with at least one operator; where the fleet of UAVs above the threshold altitude are in communication with the first computing device monitored by at least one operator such that a ratio of operators to UAVs above the threshold altitude exceeds a 1:1 ratio; and where the first UAV below the threshold altitude is in communication with the second computing device monitored by at least one operator such that a ratio of operators to UAVs below the threshold altitude does not exceed the 1:1 ratio.
Embodiments include one or more high altitude, long endurance (HALE) unmanned aircraft capable of persistent station-keeping having one or more electromagnetic (IR/Visual/RF) sensor elements or suites for purposes of survey and/or signal gathering. Embodiments include one or more high altitude, long endurance (HALE) unmanned aircraft capable of persistent station-keeping having a directable laser. Embodiments include a group of four or more high altitude, long endurance (HALE) unmanned aircraft configured as GPS repeaters.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G01S 19/11 - Systèmes de positionnement par satellite à radiophares émettant des messages horodatés, p.ex. GPS [Système de positionnement global], GLONASS [Système global de navigation par satellite] ou GALILEO Éléments coopérants; Interaction ou communication entre les différents éléments coopérants ou entre les éléments coopérants et les récepteurs fournissant des signaux de positionnement supplémentaires dédiés les éléments coopérants étant des pseudolites ou des répétiteurs de signaux de systèmes de positionnement par satellite à radiophares
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
A method of migrating unmanned aerial vehicle (UAV) operations between geographic survey areas, including: uploading a first plurality of flight missions into a first UAV pod; deploying the UAV pod; autonomously launching the UAV from the UAV pod a plurality of times to perform the first plurality of flight missions; providing first survey data from the UAV to the UAV pod; autonomously migrating the UAV from the first UAV pod to a second UAV pod; receiving a second plurality of flight missions in a second UAV pod; providing the UAV with one of the second plurality of flight missions from the second UAV pod; autonomously launching the UAV from the second UAV pod a plurality of times to perform the second plurality of flight missions; and providing a second survey data from the UAV to the second UAV pod; where the autonomous migrating of the UAV to accomplish the first and second survey data happens autonomously and without active human intervention.
B60L 53/30 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange d'éléments d’emmagasinage d'énergie dans les véhicules électriques - Détails de construction des stations de charge
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64U 50/13 - Propulsion utilisant des soufflantes ou des hélices externes
B64U 50/19 - Propulsion utilisant des moteurs électriques
B64U 70/80 - Décollage ou atterrissage verticaux, p. ex. utilisant des fusées
B64U 80/70 - Transport ou stockage spécialement adaptés aux véhicules aériens sans pilote dans des réceptacles
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
G06T 11/60 - Edition de figures et de texte; Combinaison de figures ou de texte
A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.
A method of assembling a delivery payload assembly configured to be deployed from an aircraft and travel along a flight path to a predetermined landing destination includes attaching a tail-kit assembly to a first end of a payload, the tail-kit assembly including a rotor blade assembly including a plurality of rotor blades having a central axis of rotation, and a flight control and navigation system configured to control a collective pitch angle of each of the plurality of rotor blades of the rotor blade assembly, configured to control an axial thrust force of the rotor blade assembly, the axial thrust force being at an angle with respect to the central axis of rotation of the rotor blade assembly, and configured to navigate the delivery payload assembly along the flight path to the predetermined landing destination. The method further includes removing the tail-kit assembly from the payload after the payload is delivered to the predetermined landing destination.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.
In one implementation, a method for a solar cell array is provided, the method includes emitting a communication message from the solar cell array by reverse biasing the solar cell array so as to cause at least a portion of the solar array to emit a detectable amount of radiation corresponding to the communication message. In one embodiment a solar cell array circuit is provided including a solar string comprising a plurality of solar cells coupled together, a charge storage device coupled to a power bus, and a bidirectional boost-buck converter having a first and second pair of MOSFETs connected in series between positive and negative rails of the power bus with an inductor coupled from between the first and second paired MOSFETs to a charging output of the solar string.
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.
Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.
An electric motor controller system for modulating requested motor torque via oscillating the instantaneous torque, including a bi-stable torque controller; a proportional-integral (PI) velocity controller a proportional-integral-differential (PID) position controller; and sinusoidal zero-velocity table mapping.
H02P 6/10 - Dispositions pour commander l'ondulation du couple, p.ex. en assurant une ondulation réduite du couple
B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p.ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désirées; Adaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p.ex. vitesse, couple, variation programmée de la vitesse
64.
Systems And Methods For Distributed Control Computing For A High Altitude Long Endurance Aircraft
Systems, devices, and methods including a first flight control computer (FCC) of two or more FCCs; a second FCC of the two or more FCCs; at least one selector in communication with the first FCC; and at least one watchdog window in communication with the at least one selector, where the at least one watchdog window monitors a performance of the first FCC based on an electrical pulse emitted by the FCC; where the at least one watchdog window is configured to detect a fault pulse of the electrical pulse emitted by the first FCC; and where the selector is configured to toggle to the second FCC based on the detected fault pulse emitted by the first FCC.
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
B64D 43/00 - Aménagements ou adaptations des instruments
65.
Methods of climb and glide operations of a high altitude long endurance aircraft
Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV); at least one battery pack comprising at least one battery; and at least one motor of the at least one UAV, where the at least one battery is configured to transfer energy to the at least one motor; where power from the at least one motor is configured to ascend the at least one UAV to a second altitude when the at least one battery is at or near capacity, and where the second altitude is higher than the first altitude; and where power from the at least one motor is configured to descend the at least one UAV to the first altitude after the Sun has set to conserve energy stored in the at least one battery.
G05D 1/04 - Commande de l'altitude ou de la profondeur
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64U 101/00 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques
66.
Airframe-mounted package launching system, package launching device and method of operation thereof
An airframe-mounted package launching system including a package launching device mounted in an interior portion of an airframe structure proximate an external airframe opening, the package launching device including a launch bed configured to support a package during a launching process, and a launch assembly configured to impart a launching force to the supported package on the launch bed during the launching process. The launch assembly includes a launch carriage configured to translate under an applied force from a first locked position toward a second stopped position during the launching process, and a trigger assembly configured to hold the launch carriage in the first locked position, release the launch carriage from the first locked position when the trigger assembly receives a trigger input thereby initiating the launching process, retrieve the launch carriage from the second stopped position during a retrieval process, and translate, during the retrieval process, the launch carriage against the applied force into the first locked position.
The present disclosure provides systems and methods for delivery using unmanned aerial vehicles (UAVs). In an aspect, the present disclosure provides an unmanned aircraft system, comprising: a communications unit; and a UAV comprising: a non-transitory computer-readable medium; a lift system comprising lift mechanisms to propel the UAV; a sensor system to obtain sensor information related to the UAVs environment; a processor to control operation of the lift system and the sensor system; an object detection module to detect potential mobile landing structures within the UAVs environment based on the sensor information; a mobile landing area recognition module to identify a mobile landing area on a mobile landing structure based on the sensor information; and a navigation module to estimate a real-time state of the mobile landing area based on the sensor information or the mobile landing area and to land the UAV onto the mobile landing area.
Systems, devices, and methods including an unmanned aerial vehicle (UAV); one or more inner wing panels of the UAV; one or more outer wing panels of the UAV; at least one inboard propeller attached to at least one engine disposed on the one or more inner wing panels; at least one tip propeller attached to at least one engine disposed on the one or more outer wing panels; at least one microcontroller configured to: determine an angular position of the at least one inboard propeller; and send a signal to halt rotation of the at least one inboard propeller such that the at least one inboard propeller is held in an attitude that provides for clearance of the propeller blade to the ground upon landing.
A system having: a processor and addressable memory, where the processor is configured to: receive a geographic data defining a selected geographical area; receive an operating mode associated with the selected geographical area, where the received operating mode restricts at least one of: a viewing of a UAV data and a recording of the UAV data by at least one user device; and broadcast the UAV data to the at least one user device based on the selected geographical area and the received operating mode.
H04N 7/18 - Systèmes de télévision en circuit fermé [CCTV], c. à d. systèmes dans lesquels le signal vidéo n'est pas diffusé
G06F 16/29 - Bases de données d’informations géographiques
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
G08G 1/04 - Détection du mouvement du trafic pour le comptage ou la commande utilisant des détecteurs optiques ou ultrasonores
H04N 5/232 - Dispositifs pour la commande des caméras de télévision, p.ex. commande à distance
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
H04N 5/77 - Circuits d'interface entre un appareil d'enregistrement et un autre appareil entre un appareil d'enregistrement et une caméra de télévision
In one possible embodiment, a motor winding is provided having a high density multi-conductor wire bundle with a compacted Litz wire bundle. The compacted Litz wire bundle has a serpentine configuration with a central portion having compacted Litz wire and end turns having non-compacted Litz wire.
H02K 3/14 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre disposés dans des encoches avec des conducteurs transposés, p.ex. des conducteurs torsadés
H02K 3/30 - Enroulements caractérisés par leur matériau d'isolement
H02K 3/32 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement
H02K 3/47 - Enroulements à espace d'air, c. à d. enroulements ne comportant pas de noyau de fer
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
H02K 9/02 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/14 - Dispositions de refroidissement ou de ventilation dans lesquels l'agent de refroidissement gazeux circule entre l'enveloppe de la machine et une chemise extérieure
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
H02K 16/02 - Machines avec un stator et deux rotors
H02K 21/12 - Moteurs synchrones à aimants permanents; Génératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants
A method and system including: an aerial vehicle including: a first camera comprising a first sensor having at least red, green, and blue color channels, where the blue color channel is sensitive to near-infrared (NIR) wavelengths; a first optical filter disposed in front of the first sensor, wherein the first optical filter is configured to block wavelengths below green, between red and NIR, and longer wavelength NIR; a processor having addressable memory in communication with the first camera, where the processor is configured to: capture at least one image of vegetation from the first camera; provide red, green, and NIR color channels from the captured image from the first camera; and determine at least one vegetative index based on the provided red, green, and NIR color channels.
G06V 10/143 - Détection ou éclairage à des longueurs d’onde différentes
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
B64U 70/80 - Décollage ou atterrissage verticaux, p. ex. utilisant des fusées
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
72.
Methods and systems for cloud-based management of images captured by aerial vehicles
Systems, devices, and methods for receiving image data; transferring the captured image data to a server having a processor and addressable memory via a network-connected computing device; storing the captured image data on the server; generating captured image metadata based on the stored captured image data; providing access to the captured image data and captured image metadata via an image management component; displaying, by the image management component, the captured image data; and filtering, by the image management component, the captured image data based on the generated captured image metadata.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 70/80 - Décollage ou atterrissage verticaux, p. ex. utilisant des fusées
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
G06F 16/58 - Recherche caractérisée par l’utilisation de métadonnées, p.ex. de métadonnées ne provenant pas du contenu ou de métadonnées générées manuellement
G06F 21/56 - Détection ou gestion de programmes malveillants, p.ex. dispositions anti-virus
73.
Disbursement system for an unmanned aerial vehicle
A dispersement system for a UAV is provided. The dispersement system may include a plurality of dispersement nozzles operable to dispense an agricultural product at variable flowrates, a flow controller responsive to instructions and operable to regulate a volume of the agricultural product dispensed by the dispersement nozzles, and a control system. The control system may include a plurality of sensors operable to monitor a plurality of flight parameters and a processing unit configured to model an effect of the plurality of flight parameters on first flow control instructions corresponding to a prescription coverage of the agricultural product and calculate and output modulated flow control instructions to the flow controller. The control system may modulate the first control instructions to change a flowrate of one or more of the plurality of dispersement nozzles to achieve an actual coverage of the agricultural product that is closer to the prescription coverage.
Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.
H01B 7/22 - Fils rubans ou métalliques, p.ex. d'acier
F41F 1/08 - Canons à plusieurs tubes, p.ex. canons bi-tubes
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 50/15 - Propulsion utilisant des échappements de combustion autres que les turboréacteurs ou les réacteurs à double flux, p. ex. des fusées, des statoréacteurs, des statoréacteurs à combustion supersonique ou pulsée
75.
Voronoi cropping of images for post field generation
A method and system including: defining a geographic area; receiving a plurality of images; determining a plurality of image points; partitioning the geographic area into a plurality of image regions based on the plurality of image points; and stitching the plurality of images into a combined image based on the plurality of image regions.
G06T 7/174 - Découpage; Détection de bords impliquant l'utilisation de plusieurs images
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
76.
Machine to machine targeting maintaining positive identification
A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64D 1/04 - Largage ou éjection d'objets les objets étant explosifs, p.ex. des bombes
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
F41G 7/20 - Systèmes de commande de guidage pour missiles autopropulsés basés sur une observation permanente de la position de la cible
F41G 9/00 - Systèmes de commande des missiles ou projectiles, non prévus ailleurs
77.
Methods and systems for determining flight plans for vertical take-off and landing (VTOL) aerial vehicles
Systems, devices, and methods for receiving, by a processor having addressable memory, data representing a geographical area for imaging by one or more sensors of an aerial vehicle; determining one or more straight-line segments covering the geographical area; determining one or more waypoints located at an end of each determined straight-line segment, where each waypoint comprises a geographical location, an altitude, and a direction of travel; determining one or more turnarounds connecting each of the straight-line segments, where each turnaround comprises one or more connecting segments; and generating, by the processor, a flight plan for the aerial vehicle comprising: the determined one or more straight-line segments and the determined one or more turnarounds connecting each straight-line segment.
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
78.
Safety System for Operation of an Unmanned Aerial Vehicle
Systems, devices, and methods for a safety system including: selecting an unmanned aerial vehicle (UAV) command on a controller, the controller comprising a first processor with addressable memory; presenting a first activator and a second activator on a display of the controller for the selected UAV command, wherein the second activator is a slider; and sending the UAV command to a UAV if the first activator and the second activator are selected, the UAV comprising a second processor with addressable memory.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
79.
Methods and systems for utilizing dual global positioning system (GPS) antennas in vertical take-off and landing (VTOL) aerial vehicles
Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.
A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having a UAV pod processor and a UAV selectively enclosed in the UAV pod, the UAV having only two rotors.
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
An unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having an open position and a closed position, the closed position establishing an interior that is weather resistant to an environment external to the UAV pod and a vertical takeoff and landing (VTOL) UAV enclosed in the UAV pod so that the UAV pod in the closed position provides a weather resistant interior for the VTOL UAV.
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 5/12 - Surfaces stabilisatrices réglables pour escamotage contre ou à l'intérieur du fuselage ou du fuseau-moteur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 9/36 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 5/12 - Surfaces stabilisatrices réglables pour escamotage contre ou à l'intérieur du fuselage ou du fuseau-moteur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 9/36 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 30/12 - Ailes variables ou détachables, p. ex. ailes à flèche réglable
B64U 70/00 - Dispositions pour le lancement, le décollage ou l'atterrissage
B64U 101/15 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à la guerre conventionnelle ou électronique
B64C 9/00 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction
In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
H04B 1/3822 - TRANSMISSION - Détails des systèmes de transmission non caractérisés par le milieu utilisé pour la transmission Émetteurs-récepteurs, c. à d. dispositifs dans lesquels l'émetteur et le récepteur forment un ensemble structural et dans lesquels au moins une partie est utilisée pour des fonctions d'émission et de réception spécialement adaptés à l'utilisation dans des véhicules
A system and method for transmitting still images and a video feed from an unmanned aerial vehicle to a ground station is disclosed. The system includes an aircraft including a digital video camera to capture still images and video frames of an object. A video encoder is coupled to the camera to provide a video output including video packets. A file server is coupled to the camera to provide a still image output including image data packets. A multiplexer is coupled to the video output and the still image output. The multiplexer produces a data transmission including the video packets and the image data packets. A transmitter sends the data transmission to the ground station. The ground station receives the data transmission and demultiplexes the packets into separate video and image data packets. The ground control station may select the ratio the video stream images in relation to the still image to be transmitted from the aircraft.
H04N 5/232 - Dispositifs pour la commande des caméras de télévision, p.ex. commande à distance
H04N 21/236 - Assemblage d'un flux multiplexé, p.ex. flux de transport, en combinant un flux vidéo avec d'autres contenus ou données additionnelles, p.ex. insertion d'une adresse universelle [URL] dans un flux vidéo, multiplexage de données de logiciel dans un flu; Remultiplexage de flux multiplexés; Insertion de bits de remplissage dans le flux multiplexé, p.ex. pour obtenir un débit constant; Assemblage d'un flux élémentaire mis en paquets
H04N 21/434 - Désassemblage d'un flux multiplexé, p.ex. démultiplexage de flux audio et vidéo, extraction de données additionnelles d'un flux vidéo; Remultiplexage de flux multiplexés; Extraction ou traitement de SI; Désassemblage d'un flux élémentaire mis en paquets
Disclosed herein are system and method for controlling an unmanned aerial vehicle (UAV) tethered from a mobile platform, the UAV system comprising: a UAV comprising one or more sensors, and one or more propellers; a tether attached to the UAV and to the mobile platform; a digital processing device comprising an operating system configured to perform executable instructions and a memory; and a computer program including instructions executable by the digital processing device to automatically control the UAV relative to the mobile platform comprising: a software module identifying the mobile platform; a software module estimating a real-time state of the mobile platform; and a software module automatically controlling three-dimensional real-time motion of the UAV based on the real-time state estimation of the mobile platform and data collected from the one or more sensors, such that the UAV is maintained at a predetermined position relative to the mobile platform.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64F 3/02 - Installations au sol spécialement adaptées aux aéronefs captifs avec dispositifs permettant de fournir à l'aéronef une alimentation électrique pendant le vol
H04W 4/40 - Services spécialement adaptés à des environnements, à des situations ou à des fins spécifiques pour les véhicules, p.ex. communication véhicule-piétons
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G01L 5/04 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de la tension dans les éléments flexibles, p.ex. dans les cordages, les câbles, les fils métalliques, les filaments, les courroies ou les bandes
87.
Systems and devices for an RF signal carrying cable of a multi-pack launcher system
Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.
Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.
In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.
In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.
A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.
B60K 1/04 - Agencement ou montage des ensembles de propulsion électriques des dispositifs d'emmagasinage de l'énergie électrique pour la propulsion
B60K 1/00 - Agencement ou montage des ensembles de propulsion électriques
B64D 27/00 - Disposition du montage des groupes moteurs sur aéronefs; Aéronefs ainsi caractérisés
B63H 21/17 - Aménagements de l'appareil moteur de propulsion ou de certains de ses éléments pour utilisation à bord des navires le navire étant actionné par moteurs par moteur électrique
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
B60K 17/356 - Agencement ou montage des transmissions sur les véhicules pour entraînement simultané des roues avant et arrière, p.ex. véhicules à quatre roues motrices comportant un moteur à fluide ou électrique pour entraîner une ou plusieurs roues
In one embodiment, a magnet array and ironless winding for a motor is provided which has an array of permanent magnets being arranged such that flux from the permanent magnets reinforce on one side of the array and substantially cancel on an opposite side of the array, the array further includes flux concentrators forming poles on the reinforcing side of the array, and such that a magnetic moment at the poles is oriented generally perpendicular to the reinforcing side of the array, the winding being adjacent to the array and comprising conductor bundles having a generally rectangular cross-section arranged such that a long side of the generally rectangular cross-section is transverse to a direction of magnetic field lines at the poles.
An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.
Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.
B64C 9/16 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction formant des fentes à l'arrière de l'aile
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 13/38 - Dispositifs de transmission avec amplification de puissance
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 3/24 - Structures moulées ou venues de fonderie
B64C 3/36 - Structures adaptées pour réduire les effets de l'échauffement aérodynamique ou les effets d'un échauffement externe d'une autre origine
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
95.
Interactive weapon targeting system displaying remote sensed image of target area
Systems, devices, and methods for determining a predicted impact point of a selected weapon and associated round based on stored ballistic information, provided elevation data, provided azimuth data, and provided position data.
In one possible embodiment, a motor winding is provided having a high density multi-conductor wire bundle with a compacted Litz wire bundle. The compacted Litz wire bundle has a serpentine configuration with a central portion having compacted Litz wire and end turns having non-compacted Litz wire.
H02K 3/14 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre disposés dans des encoches avec des conducteurs transposés, p.ex. des conducteurs torsadés
H02K 3/47 - Enroulements à espace d'air, c. à d. enroulements ne comportant pas de noyau de fer
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
H02K 16/02 - Machines avec un stator et deux rotors
H02K 9/14 - Dispositions de refroidissement ou de ventilation dans lesquels l'agent de refroidissement gazeux circule entre l'enveloppe de la machine et une chemise extérieure
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/02 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
H02K 3/30 - Enroulements caractérisés par leur matériau d'isolement
H02K 3/32 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement
H02K 21/12 - Moteurs synchrones à aimants permanents; Génératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants
97.
Dynamic transmission control for a wireless network
In one possible embodiment, a wireless network with dynamic transmission control is provided that includes a multiple of nodes. The nodes include an arbiter and multiple client nodes. The arbiter is configured to control an operation of the client nodes by defining communications operation cycles and allocating a bandwidth to each of the client nodes on a cycle by cycle basis in response to requests for bandwidth from the client nodes.
H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p.ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 5/12 - Surfaces stabilisatrices réglables pour escamotage contre ou à l'intérieur du fuselage ou du fuseau-moteur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 9/36 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A method of migrating unmanned aerial vehicle (UAV) operations between geographic survey areas, including: uploading a first plurality of flight missions into a first UAV pod; deploying the UAV pod; autonomously launching the UAV from the UAV pod a plurality of times to perform the first plurality of flight missions; providing first survey data from the UAV to the UAV pod; autonomously migrating the UAV from the first UAV pod to a second UAV pod; receiving a second plurality of flight missions in a second UAV pod; providing the UAV with one of the second plurality of flight missions from the second UAV pod; autonomously launching the UAV from the second UAV pod a plurality of times to perform the second plurality of flight missions; and providing a second survey data from the UAV to the second UAV pod; where the autonomous migrating of the UAV to accomplish the first and second survey data happens autonomously and without active human intervention.
B60L 53/30 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange d'éléments d’emmagasinage d'énergie dans les véhicules électriques - Détails de construction des stations de charge
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64F 1/22 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manœuvre des aéronefs
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
Described is a method of delivery for cargo or goods from an aerial vehicle (mothership) to a designated ground delivery location via the use of a direct air shipping (DASH) package. For example an aerial vehicle may be an airplane or helicopter that remains at altitude with a DASH packaged stowed for deployment. As the mothership travels in the vicinity of the designated location the DASH package flight control computer (flight controller) calculates a preferred travel trajectory based upon the aerodynamic properties of the package and location relative to the designated delivery location such as a small delivery pad located on a patio of a home. When the mothership transits through a calculated release point the DASH package disengages the mothership. As the DASH package descends it may increase accuracy relative to the designated delivery location by altering aerodynamic properties to maintain the preferred travel trajectory and decreasing landing zone size requirements and increasing precision of delivery. To reduce the impact force at landing the designated delivery location and/or the DASH package may contain a net, airbag, parachute or similar device to provide a suitably soft landing suitable for commercial home delivery.
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